Method for modifying a shroud and blade

Abstract

A method for modifying an airfoil shroud located at a tip of an airfoil is provided. A locating step locates a reference location in a first end edge. The reference location includes a portion of a fillet. A seal rail extends circumferentially along a radially outer surface of the airfoil shroud. The fillet extends along the radially outer surface and is positioned directly adjacent to the seal rail. A forming step forms a compound relief cut in the fillet without performing a weld process on the airfoil shroud to remove the reference location. The compound relief cut has a first cut having a first radius extending from the seal rail towards the first end edge, and a second cut having a second radius extending from an end of the first cut to the first end edge. Modifying the airfoil shroud is complete following forming the compound relief cut.

Description

BACKGROUND OF THE INVENTION[0001]The subject matter disclosed herein relates to turbine engines. More particularly, the subject matter relates to modifying of turbine parts.[0002]In a gas turbine, a compressor provides pressurized air to one or more combustors wherein the air is mixed with fuel and burned to generate hot combustion gas. These gases flow downstream to a turbine that extracts energy therefrom to produce a mechanical energy output as well as power to drive the compressor. Over time, turbine parts, such as blades or nozzles, may experience fatigue, due to extreme conditions within the turbine, including high temperatures and pressures caused by flow of hot gas. In particular, certain turbine parts, such as blades located on a turbine rotor, may experience fatigue that requires servicing or replacement.[0003]In cases where defect locations in fatigued areas utilize welding or other heat-based operations, the repair process may further fatigue the local area. Thus, repair...

AI Technical Summary

Benefits of technology

The patent text describes a method for modifying an airfoil shrimp by creating a compound relief cut using a fillet and a seal rail on the outer surface of the shrimp. This cut includes two different radii, with the second radius larger than the first. This method does not require a weld process and allows for the creation of a precise and strong fix on the outer surface of the shrimp. This compound relief cut can be used to attach various components to the shrimp, such as blades or other parts, making the attachment process more robust. The technical effects of this patent include improved attachment of components to the airfoil shrimp and increased strength of the attachment.

Problems solved by technology

Over time, turbine parts, such as blades or nozzles, may experience fatigue, due to extreme conditions within the turbine, including high temperatures and pressures caused by flow of hot gas.

In particular, certain turbine parts, such as blades located on a turbine rotor, may experience fatigue that requires servicing or replacement.

In cases where defect locations in fatigued areas utilize welding or other heat-based operations, the repair process may further fatigue the local area.

Thus, repair of some defect locations occurring due to wear and tear is not feasible.

Replacement of these parts can be costly, especially if fatigue in selected areas occurs in several parts, such as blades on a rotor wheel.

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